MR Actuator Backup for Single Hydraulic Rotorcraft Flight Control
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Solution Overview
Problem
Aircraft, particularly rotorcraft, face challenges with dual hydraulic systems that increase weight, cost, and space requirements due to dual actuators for boosting pilot flight control inputs, necessitating a more efficient and compact hydraulic control system.
Innovation Solution
Implementing a single hydraulic system with a magnetorheological (MR) actuator that provides both autopilot/trim functions and force assistance in case of hydraulic failure, using MR fluid to modulate force feedback and reduce pilot effort.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a dual hydraulic system with dual actuators is used for boosting pilot flight control inputs, then reliability and force assistance are improved, but weight, cost, and space requirements increase
Solution Approach 1:
The patent combines autopilot/trim functions and force assistance functions into a single hydraulic actuator system. The single actuator performs multiple functions that traditionally required separate dual actuators, thereby reducing weight while maintaining reliability through functional integration rather than redundant hardware
Solution Approach 2:
The single hydraulic actuator is designed to provide multiple functions: normal force assistance during flight operations, autopilot/trim control, and backup force assistance during hydraulic failures. This multi-functional design eliminates the need for separate dedicated actuators for each function, reducing overall system weight and space requirements
2Reliability
If a dual hydraulic system with dual actuators is used for boosting pilot flight control inputs, then reliability and force assistance are improved, but device complexity increases
Solution Approach 1:
The patent merges multiple hydraulic control functions into a single actuator system with integrated control logic. The flight control computer coordinates autopilot, trim, and force assistance functions through one actuator, simplifying the hydraulic manifold and reducing the number of hydraulic lines, valves, and components required compared to dual independent actuator systems
3Weight of moving object
If a single hydraulic system is used to reduce weight and space, then device complexity and weight are reduced, but reliability and force assistance capability deteriorate
Solution Approach 1:
The single hydraulic actuator is designed as a universal system that provides normal force assistance, autopilot/trim control, and emergency backup force assistance. This multi-functional capability ensures that despite having only one actuator, the system maintains reliability across different operational scenarios and failure modes
Solution Approach 2:
The system includes self-diagnostic capabilities where the flight control computer monitors the single hydraulic actuator's performance and automatically detects failures. Upon detecting a failure, the system self-adjusts by reconfiguring the MR actuator to provide force assistance, eliminating the need for manual intervention or backup hardware
4Volume of moving object
If a single hydraulic system is used to reduce space requirements, then volume and device complexity are reduced, but reliability and force assistance capability deteriorate
Solution Approach 1:
The patent consolidates multiple hydraulic control functions into a single compact actuator system, reducing the volume occupied by hydraulic components, manifolds, and associated hardware. The integrated design maintains full functional capability including force assistance and autopilot/trim operations within a smaller footprint
Solution Approach 2:
The single hydraulic actuator performs multiple functions including force assistance, autopilot control, and trim operations, ensuring that the reduced-volume system does not sacrifice reliability or operational capability. The MR actuator provides adaptive force modulation to maintain performance across different flight conditions despite the simplified hardware architecture
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The MR actuator enhances flight control efficiency and safety by reducing weight and space requirements while ensuring smooth transitions between flight conditions without exceptional piloting skills, even in hydraulic system failures.
Implementation Method 1
an MR actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device
Implementation Method 2
a single hydraulic system with a magnetorheological (MR) actuator that provides both autopilot/trim functions and force assistance
Data Source
AI summary
One embodiment is an aircraft comprising a fuselage; a rotor system connected to the fuselage and comprising at least one rotor blade; a pilot input device; a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device; and a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; wherein subsequent to detection of a failure of the single hydraulic servo actuator, the MR actuator is caused to provide force assistance to the pilot input device.